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GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 393 AIRFOIL (goe393-il)
Reynolds number: 100,000
Max Cl/Cd: 55.91 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe393-il-100000.txt
Download as CSV file: xf-goe393-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 393 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4583   0.10800   0.10323   0.0139   1.0000   0.0705
  -8.000  -0.4577   0.10698   0.10228   0.0089   1.0000   0.0725
  -7.750  -0.4529   0.10664   0.10199  -0.0023   1.0000   0.0732
  -7.500  -0.4439   0.10067   0.09606  -0.0018   1.0000   0.0740
  -7.250  -0.4333   0.09505   0.09045   0.0034   1.0000   0.0755
  -7.000  -0.4222   0.09134   0.08676   0.0031   1.0000   0.0775
  -6.750  -0.4103   0.08796   0.08340   0.0008   1.0000   0.0799
  -6.500  -0.3961   0.08471   0.08015  -0.0035   1.0000   0.0832
  -6.250  -0.3609   0.08390   0.07915  -0.0227   1.0000   0.0867
  -6.000  -0.3588   0.07744   0.07284  -0.0163   1.0000   0.0880
  -5.750  -0.3471   0.07361   0.06906  -0.0149   1.0000   0.0902
  -5.500  -0.3299   0.07024   0.06568  -0.0167   1.0000   0.0932
  -5.250  -0.3034   0.06720   0.06255  -0.0228   1.0000   0.0985
  -5.000  -0.2714   0.06366   0.05883  -0.0308   1.0000   0.1013
  -4.750  -0.2611   0.05971   0.05501  -0.0286   1.0000   0.1036
  -4.500  -0.2416   0.05678   0.05208  -0.0295   1.0000   0.1086
  -4.250  -0.2031   0.05411   0.04911  -0.0371   1.0000   0.1154
  -4.000  -0.1895   0.05048   0.04560  -0.0361   1.0000   0.1174
  -3.750  -0.1709   0.04787   0.04304  -0.0364   1.0000   0.1215
  -3.500  -0.1442   0.04631   0.04124  -0.0399   1.0000   0.1296
  -3.250  -0.1194   0.04289   0.03798  -0.0423   0.9879   0.1342
  -2.750  -0.0121   0.03634   0.03096  -0.0565   0.9437   0.1612
  -2.500   0.0281   0.03391   0.02832  -0.0598   0.9145   0.1759
  -2.250   0.0590   0.03193   0.02617  -0.0608   0.8858   0.1920
  -2.000   0.0847   0.03043   0.02445  -0.0607   0.8603   0.2192
  -1.750   0.1062   0.02887   0.02279  -0.0596   0.8382   0.2501
  -1.500   0.1534   0.00975   0.00254  -0.0581   0.7919   0.1295
  -1.250   0.1908   0.02318   0.01500  -0.0607   0.8046   0.1138
  -1.000   0.2182   0.02183   0.01328  -0.0600   0.7877   0.1138
  -0.750   0.2436   0.02084   0.01222  -0.0595   0.7718   0.1207
  -0.500   0.2716   0.02011   0.01105  -0.0586   0.7571   0.1281
  -0.250   0.2980   0.01915   0.00998  -0.0580   0.7432   0.1374
   0.000   0.3250   0.01850   0.00910  -0.0572   0.7297   0.1563
   0.250   0.3512   0.01798   0.00858  -0.0568   0.7160   0.1781
   0.500   0.3777   0.01784   0.00837  -0.0563   0.7026   0.2015
   0.750   0.4044   0.01760   0.00812  -0.0558   0.6898   0.2164
   1.000   0.4307   0.01733   0.00790  -0.0552   0.6774   0.2251
   1.250   0.4571   0.01721   0.00774  -0.0544   0.6655   0.2333
   1.500   0.4837   0.01717   0.00765  -0.0538   0.6543   0.2463
   1.750   0.5105   0.01713   0.00768  -0.0534   0.6419   0.2625
   2.000   0.5374   0.01711   0.00777  -0.0531   0.6303   0.2878
   2.250   0.5694   0.01565   0.00776  -0.0534   0.6192   1.0000
   2.500   0.5963   0.01598   0.00781  -0.0527   0.6091   1.0000
   2.750   0.6232   0.01636   0.00811  -0.0524   0.5977   1.0000
   3.000   0.6499   0.01677   0.00845  -0.0521   0.5880   1.0000
   3.250   0.6764   0.01713   0.00870  -0.0515   0.5792   1.0000
   3.500   0.7030   0.01758   0.00918  -0.0513   0.5686   1.0000
   3.750   0.7295   0.01800   0.00957  -0.0509   0.5608   1.0000
   4.000   0.7561   0.01849   0.01011  -0.0507   0.5518   1.0000
   4.250   0.7824   0.01894   0.01058  -0.0504   0.5427   1.0000
   4.500   0.8081   0.01906   0.01062  -0.0494   0.5315   1.0000
   4.750   0.8336   0.01904   0.01055  -0.0484   0.5175   1.0000
   5.000   0.8590   0.01904   0.01055  -0.0475   0.5029   1.0000
   5.250   0.8847   0.01922   0.01081  -0.0468   0.4900   1.0000
   5.500   0.9105   0.01954   0.01125  -0.0464   0.4791   1.0000
   5.750   0.9364   0.01976   0.01154  -0.0457   0.4685   1.0000
   6.000   0.9623   0.01984   0.01162  -0.0449   0.4570   1.0000
   6.250   0.9878   0.01991   0.01178  -0.0442   0.4433   1.0000
   6.500   1.0132   0.01998   0.01197  -0.0434   0.4286   1.0000
   6.750   1.0382   0.02004   0.01216  -0.0425   0.4116   1.0000
   7.000   1.0625   0.01996   0.01222  -0.0415   0.3886   1.0000
   7.250   1.0855   0.01971   0.01195  -0.0402   0.3554   1.0000
   7.500   1.1065   0.01979   0.01205  -0.0390   0.3023   1.0000
   7.750   1.1259   0.02054   0.01254  -0.0379   0.2366   1.0000
   8.000   1.1432   0.02197   0.01360  -0.0370   0.1875   1.0000
   8.250   1.1575   0.02393   0.01522  -0.0358   0.1548   1.0000
   8.500   1.1708   0.02614   0.01730  -0.0344   0.1222   1.0000
   8.750   1.1831   0.02850   0.01945  -0.0329   0.0977   1.0000
   9.000   1.1984   0.03066   0.02159  -0.0314   0.0830   1.0000
   9.250   1.2155   0.03291   0.02369  -0.0302   0.0737   1.0000
   9.500   1.2332   0.03466   0.02571  -0.0289   0.0665   1.0000
   9.750   1.2521   0.03714   0.02804  -0.0280   0.0616   1.0000
  10.000   1.2704   0.03972   0.03098  -0.0267   0.0588   1.0000
  10.250   1.2864   0.04222   0.03378  -0.0255   0.0558   1.0000
  10.500   1.3006   0.04439   0.03611  -0.0244   0.0527   1.0000
  10.750   1.3150   0.04835   0.04011  -0.0238   0.0505   1.0000
  11.000   1.3207   0.05187   0.04408  -0.0223   0.0499   1.0000
  11.250   1.3213   0.05566   0.04832  -0.0207   0.0495   1.0000
  11.500   1.3167   0.05969   0.05275  -0.0192   0.0494   1.0000
  11.750   1.3067   0.06377   0.05717  -0.0177   0.0494   1.0000
  12.000   1.2916   0.06782   0.06150  -0.0165   0.0495   1.0000
  12.250   1.2742   0.07232   0.06624  -0.0164   0.0497   1.0000
  12.500   1.2556   0.07741   0.07154  -0.0176   0.0499   1.0000
  12.750   1.2365   0.08313   0.07745  -0.0197   0.0501   1.0000
  13.000   1.2175   0.08948   0.08395  -0.0223   0.0504   1.0000
  13.250   1.1891   0.09611   0.09088  -0.0277   0.0511   1.0000
  13.750   0.9203   0.11664   0.11195  -0.0305   0.0605   1.0000
  14.000   0.8204   0.14037   0.13566  -0.0443   0.0721   1.0000
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